JP2014000855A - Stabilizer link - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a stabilizer link and a manufacturing method thereof, capable of securing request strength of a rib, needless to say to be capable of securing request strength of a wing plate and a central support plate in a support bar.SOLUTION: A support bar 150 comprises wing plates 151 and 152, a central support plate 153 and ribs 154A-154F. In the wing plates 151 and 152 and the central support plate 153, reinforced fiber is oriented in the longitudinal direction of the support bar 150. In the ribs 154A-154F, the reinforced fiber is oriented in the vertical direction. An orientation ratio D1(%) in the longitudinal direction of a central part in the longitudinal direction of the wing plates 151 and 152, an orientation ratio D2(%) in the vertical direction of a central part in the vertical direction of the ribs 154A-154F and an orientation ratio D3 in the vertical direction of an end part in the vertical direction of the ribs 154A-154F, satisfy Expression (1). D1>D2>D3 ... Expression (1).

Description

  The present invention relates to a stabilizer link having a support bar and a method of manufacturing the same, and more particularly to an improvement of a resin support bar.

  The stabilizer link is a ball joint component that connects the arm or strut of the suspension device and the stabilizer device. FIG. 1 is a perspective view illustrating a schematic configuration on the front wheel side of the vehicle. The suspension device 1 is provided on the left and right tires 4 and includes an arm 11 and a cylinder 12. The lower end portion of the arm 11 is fixed to a bearing portion that supports the shaft of the tire 4, and the cylinder 12 can be elastically displaced with respect to the arm 11. The arm 11 is provided with a bracket 13 to which the stabilizer link 3 is attached. The suspension device 1 supports the weight of the vehicle body added to the tire 4. The stabilizer device 2 includes a bar 21 having a substantially U-shape, and is attached to the vehicle body via a bush 22. The stabilizer device 2 ensures the roll rigidity of the vehicle.

  The stabilizer link 3 is provided at the end of the bracket 13 of the suspension device 1 and the bar 21 of the stabilizer device 2, and the stabilizer links 3 are connected to each other by a support bar 70. The stabilizer link 3 transmits a load generated when the suspension device 1 receives an input from the road surface to the stabilizer device 2.

  FIG. 2 is a side sectional view showing a specific example of a configuration of a part of the stabilizer link 3. The stabilizer link 3 includes a ball stud 30, a ball seat 40, a housing 50, and a dust cover 60.

  The ball stud 30 has a stud portion 31 and a ball portion 32 that are integrally formed. The stud portion 31 has a taper portion 33, a straight portion 34, and a screw portion 35. The tapered portion 33 is formed at the upper end portion of the ball portion 32. A flange portion 36 and a convex portion 37 are formed at the upper end portion and the lower end portion of the linear portion 34. An upper fixing portion 61 of the dust cover 60 is in contact with and fixed between the flange portion 36 and the convex portion 37 in the linear portion 34. The screw portion 35 of the stabilizer link 3 on the suspension device 1 side is fixed to the bracket 13 of the arm 11 by screw fastening, and the screw portion 35 of the stabilizer link 3 on the stabilizer device 2 side is fixed to the bar 21 by screw fastening. .

  The ball seat 40 and the housing 50 constitute a shaft support member that universally supports the ball stud 30. The ball portion 32 of the ball stud 30 is press-fitted into the ball seat 40. The housing 50 accommodates the ball seat 40. The lower fixing portion 62 of the dust cover 60 is held between the ball seat 40 and the flange portions 41 and 51 of the housing 50. A heat caulking portion 42 is formed on the bottom surface of the ball seat 40. The heat caulking portion 42 protrudes through the hole 52 at the bottom of the housing 50, and the tip end portion engages with the lower surface portion of the housing 50 (for example, Patent Document 1).

  Iron is used as the material of the housing 50 and the support bar 70. The housing 50 and the support bar 70 are molded separately, and the support bar 70 is connected to the housing 50 by welding such as resistance welding.

  In recent years, in order to reduce the weight, it has been proposed to use a resin as the material of the support bar and to form the support bar by injection molding. Resin used in injection molding usually contains reinforcing fibers such as glass fiber fine fibers.

  In the stabilizer link 5 shown in FIG. 3, for example, a resin housing 80 and a support bar 90 are integrally formed. As shown in FIG. 3A, the support bar 90 includes an upper wing plate 91, a lower wing plate 92, a center support plate 93, and ribs 94A and 94B. The wing plates 91 and 92 and the central support plate 93 are portions for securing the strength of the support bar 90 in the longitudinal direction, and extend in the longitudinal direction to connect the stabilizer links 5 to each other. The upper wing plate 91 and the lower wing plate 92 are provided at the upper end portion and the lower end portion of the center support plate 93 and project in the horizontal direction with respect to the center support plate 93 as shown in FIG. As described above, the upper wing plate 91, the lower wing plate 92, and the central support plate 93 have an I shape in a cross section perpendicular to the longitudinal direction.

  The ribs 94A and 94B are provided between the wing plates 91 and 92, and are portions for ensuring the strength in the vertical direction. The rib 94A is provided at the center in the longitudinal direction of the center support plate 93, and the ribs 94B and 94B are provided at a predetermined interval in the longitudinal direction from the rib 94A. The ribs 94 </ b> A and 94 </ b> B protrude in the horizontal direction with respect to the central support plate 93, similarly to the wing plates 91 and 92. In the stabilizer link 5, the ball seat and the bottom of the housing are fixed to each other by ultrasonic caulking. In FIG. 3, the same components as those of the stabilizer link 5 shown in FIG.

  The housing 80 and the support bar 90 are obtained by performing injection molding using a mold having a cavity having a shape corresponding to them. The cavity has a housing forming part for forming the housing 80 and a support bar forming part for forming the support bar 90. The support bar forming part is a wing plate forming part for forming the wing plates 91 and 92. And a central support plate forming portion for forming the central support plate 93 and a rib forming portion for forming the ribs 94A and 94B. In this case, the gate for injecting the resin into the cavity is located in the longitudinal direction and the horizontal center of the lower wing plate forming portion.

  In such injection molding, the resin is more likely to flow when the flow path width is larger. In the support bar 90 of the stabilizer link 5, the plate thickness t1 of the wing plates 91 and 92 (flow path width of the wing plate forming portion) is 4.2 mm, and the plate thickness t2 of the central plate 93 (flow channel width of the central plate forming portion). Is 3.2 mm, and the thicknesses t3 of the support plates 94A and 94B (flow path width of the support plate forming portion) are 2.2 mm. Thus, since the flow path width is set to become narrower in the order of the wing plate forming portion, the central plate forming portion, and the support plate forming portion, the flow of the resin in the support bar forming portion is the wing plate forming portion, It occurs in the order of the center plate forming portion and the support plate forming portion, and after the resin is filled in the wing plate forming portion and the center plate forming portion, it is filled in the support plate forming portion.

JP-A-6-117429

  When the longitudinal direction of the reinforcing fiber contained in the resin matches the required strength direction inside each plate, the strength by the reinforcing fiber can be sufficiently obtained. In the case of the wing plates 91 and 92 and the central support plate 93 having a function of preventing the buckling of the support bar 90, the required strength direction is the longitudinal direction of the support bar, and the function of preventing the wing plates 91 and 92 from falling down. In the case of the ribs 94A and 94B, the required strength direction is the vertical direction.

  The strength of each part of the support bar 90 is theoretically obtained based on the cross-sectional moment and the like. However, when the ribs 94A and 94B of the support bar 90 having the above-described configuration are examined, the ribs 94A and 94B are manufactured as follows. It has been found that the above problems may occur.

  If the flow path width of the rib forming part of the mold is too narrow, the pipe resistance increases, and the inflow of resin from the lower wing plate forming part on the gate side to the rib forming part decreases. The inflow amount of resin from the upper wing plate forming part on the opposite side increases. Therefore, the resin from the upper wing plate forming portion and the resin from the lower wing plate forming portion merge at or near the central portion in the height direction of the rib forming portion, so that defects such as weld flow may occur there. . In this case, when a turbulent flow due to a collision or the like occurs in the joint portion of the resin, the reinforcing fiber is caught in the turbulent flow, and the direction of each reinforcing fiber becomes random. Thus, since it becomes difficult to align the reinforcing fibers in the required strength direction, the required strength of the ribs 94A and 94B may not be ensured. In particular, the vertical central portions of the ribs 94A and 94B are locations where the generated stress is maximized, so the above problem is serious.

  In addition, if the flow path width of the rib forming portion of the mold is too wide, minute voids are generated in the ribs 94A and 94B, and the required strength of the ribs 94A and 94B may not be ensured. Furthermore, since the required strength direction of the ribs 94A and 94B is a vertical direction, it is desirable that the resin flow into the rib forming portion is performed from the wing plate forming portion at the time of injection molding. However, since the resin flow in the support bar forming portion occurs in the order of the wing plate forming portion, the central support plate forming portion, and the rib forming portion, the resin flows into the rib forming portion also from the central support plate forming portion. As a result, the required strength of the ribs 94A and 94B may not be ensured.

  As described above, particularly in the ribs 94A and 94B, the required strength may not be ensured.

  Accordingly, the present invention provides a stabilizer link capable of ensuring the required strength of the ribs as well as the required strength of the wing plate and the central support plate in the support bar, and a method for manufacturing the stabilizer link. It is an object.

The stabilizer link of the present invention is formed by injection molding using a resin containing reinforcing fibers, and includes a support bar for connecting housings, and the support bar includes an upper wing plate, a lower wing plate, and a central support. The plate has a plurality of ribs, and the upper wing plate, the lower wing plate, and the center support plate have an I-shape in a cross section extending in the longitudinal direction of the support bar and perpendicular to the longitudinal direction. The ribs of the upper wing plate and the lower wing plate are spaced apart from each other in the longitudinal direction. In the upper wing plate, the lower wing plate, and the central support plate, the reinforcing fibers are oriented in the longitudinal direction. In the ribs, the reinforcing fibers are oriented in the vertical direction, the longitudinal orientation ratio of the longitudinal center portion of the upper wing plate and the lower wing plate is D1 (%), and the perpendicular center portion of the rib is perpendicular. Countercurrent orientation ratio D2 (%), when the vertical orientation rate in the vertical direction end portions of the ribs was set to D3 (%), the orientation ratio D1~D3 is characterized by satisfying the formula (1).
D1>D2> D3 Formula (1)

  The direction of the stabilizer link in the present invention is described based on the case where the upper wing plate is disposed on the upper side and the lower wing plate is disposed on the lower side. For example, the ribs are formed on both the left and right sides parallel to the longitudinal direction of the central support plate. Therefore, the vertical central portion of the rib is the vertical central portion of the rib formed on each of the left and right surfaces of the central support plate. It is.

  In the present application, the orientation rate of the reinforcing fibers is defined as follows. In the case of the wing plate and the central support plate, the required strength direction is the longitudinal direction of the support bar, and in the case of the rib, the required strength direction is the vertical direction. For each part, if the angle of the reinforcing fiber with respect to the required strength direction is in the range of −45 ° or more and 45 ° or less, the reinforcing fiber is defined as oriented in the required strength direction. In the following, the reinforcing fibers oriented in the required strength direction in this way are referred to as required strength direction oriented fibers.

  The orientation ratio is a ratio DM (= number of required strength direction oriented fibers / number of oriented fibers in the required strength direction) to the total number of fibers in a predetermined region of the cross section of each part (cross section parallel to the required strength direction). Number).

  As a method for counting the total number of fibers, for example, a method of counting bright portions as fibers in a cross-sectional observation photograph obtained by SEM can be used. In this case, for example, a bright portion having a linear shape, an elliptical shape, a circular shape, or a shape close thereto can be counted as a fiber. For a bright portion of a linear shape and a substantially linear shape, when a predetermined length (for example, 0.1 mm) is a unit length u (mm) and the measured length of the fiber is v (mm), the number N is set to v / u. In this case, the number N can be obtained by rounding off after the decimal point.

In counting the number of required strength direction oriented fibers, among all the fibers counted as described above, fibers whose reinforcing fibers are in the range of −45 ° to 45 ° with respect to the required strength direction are oriented in the required strength direction. As the fibers, fibers having an aspect ratio of ^21/2 or more among such fibers are counted. The aspect ratio is the maximum length in the longitudinal direction of the bright portion with respect to the maximum length in the width direction of the bright portion (= maximum length in the longitudinal direction / maximum length in the width direction). The reason why the aspect ratio is set to 2 ^1/2 (≈1.4) is, for example, for a fiber whose angle with respect to the required strength direction is 45 ° for the fiber shown in FIG. When viewed, the cross-sectional shape is elliptical as shown in FIG. 7B, and the aspect ratio is 2 ^1/2 (≈1.4).

  In the stabilizer link of the present invention, since the resin is used as the material of the support bar, not only can the weight be reduced, but the resin contains reinforcing fibers, and the orientation of the reinforcing fibers in each plate of the support bar. Since the direction is set as follows, the strength can be secured by each plate. In the upper wing plate, lower wing plate and center support plate of the support bar, the reinforcing fibers are oriented in the longitudinal direction of the support bar, which is the required strength direction of the plates, and in the ribs, the reinforcing fibers are oriented in the vertical direction. Therefore, the strength by the reinforcing fibers can be obtained in the required strength direction of the plates.

  Here, in the stabilizer link of the present invention, the longitudinal orientation ratio D1 of the longitudinal center portion of the wing plate, the vertical orientation ratio D2 of the vertical center portion of the rib, and the vertical orientation ratio D3 of the vertical end portion of the rib are: Satisfies equation (1). Therefore, in the wing plate, the longitudinal direction orientation ratio D1 of the central portion in the longitudinal direction is set to the maximum among all the plates, so that the strength by the reinforcing fibers can be sufficiently obtained in the required strength direction (longitudinal direction). . As a result, when a compressive load is applied in the longitudinal direction of the support bar, it is possible to effectively suppress the support bar from buckling. In the rib, the vertical direction orientation ratio D2 at the center in the vertical direction is set larger than the vertical direction orientation ratio D3 at the end in the vertical direction, so that sufficient strength can be obtained from the reinforcing fibers in the required strength direction (vertical direction). be able to. As a result, the wing plate can be effectively prevented from falling.

  Various configurations can be used for the stabilizer link of the present invention. In order to sufficiently obtain the strength of the reinforcing fibers in the required strength direction of each plate, the orientation ratio can be set as follows. For example, a mode in which the vertical direction orientation ratio D2 of the central portion in the vertical direction of the rib is set to 50% or more can be used. The longitudinal direction orientation rate D1 of the longitudinal direction center part of an upper wing board and a lower wing board can use the aspect set to 60% or more. The aspect set to 60% or more can be used for the longitudinal direction orientation rate D4 of the longitudinal direction center part of a center support plate.

  In particular, in the wing plate and the central support plate, when the orientation direction of the reinforcing fibers in all the portions in the longitudinal direction coincides with the required strength direction, the strength by the reinforcing fibers can be obtained to the maximum. In the rib, when the orientation direction of the reinforcing fibers in all the vertical portions thereof matches the required strength direction, the strength of the reinforcing fibers can be obtained to the maximum. As a result, the above effects can be obtained more effectively.

  Moreover, the aspect whose content of the reinforced fiber in resin is 25 to 60 weight% can be used. An embodiment in which the resin is engineering plastic or super engineering plastic can be used.

The manufacturing method of the stabilizer link of the present invention is a specific form of the manufacturing method of the stabilizer link of the present invention. That is, in the manufacturing method of the stabilizer link of the present invention, the support bar is formed by injecting resin into the mold cavity from the gate and performing injection molding. In forming the support bar, the upper wing plate and the lower wing plate are formed. The central support plate extends in the longitudinal direction of the support bar and has an I-shape in a cross section perpendicular to the longitudinal direction, and a plurality of ribs are formed between the upper wing plate and the lower wing plate. When the plate thickness of the upper wing plate and the lower wing plate is t1, the plate thickness of the central support plate is t2, and the plate thickness of the plurality of ribs is t3, the plate thicknesses t1, t2 , T3 satisfy the expressions (1) to (3).
t1>t2> t3 Formula (2)
0.77 ≦ t2 / t1 ≦ 0.85 Formula (3)
0.77 ≦ t3 / t2 ≦ 0.85 Formula (4)

  In the manufacturing method of the stabilizer link of the present invention, the orientation direction of the reinforcing fiber of each plate is made to coincide with the required strength direction like the stabilizer link of the present invention, the longitudinal orientation ratio D1 of the longitudinal center of the wing plate, In order to control the flow of the resin so that the vertical direction orientation ratio D2 of the vertical center portion and the vertical direction orientation ratio D3 of the vertical end portion of the rib satisfy the formula (1), the upper wing plate, the lower wing plate, the center A relational expression of the thickness of each of the support plate and the rib is set.

  In the mold used in the manufacture of the stabilizer link, for example, when resin is injected from the gate, the resin flows, for example, in the support bar forming portion and the housing forming portion. In this case, the thickness t1 of the upper wing plate and the lower wing plate, the thickness t2 of the central support plate, and the thickness t3 of the plurality of ribs at the support bar forming portion through the housing forming portion so as to satisfy the formula (2). The flow of resin occurs in the order of the wing plate forming portion, the central support plate forming portion, and the rib forming portion, and the resin is filled in the rib forming portion after being filled in the wing plate forming portion and the central support plate forming portion. .

  In this case, since the wing plate contributes most to the rigidity improvement of the support bar, the upper wing plate and the lower wing plate are made thickest. For example, when a gate is provided on the wing plate forming portion side of the mold cavity, if resin is injected from the gate into the cavity, the resin flows in the longitudinal direction of the wing plate forming portion. Can be set in the longitudinal direction of the support bar. Therefore, since the orientation direction of the reinforcing fiber can be matched with the required strength direction of the wing plate, the strength by the reinforcing fiber can be sufficiently obtained.

  Here, in the manufacturing method of the stabilizer link of the present invention, the I-shaped wing plate and the central support plate are ribbed by setting the thickness of the central support plate to be thinner than the wing plate and thicker than the rib. Can be preferentially formed. In this case, for example, if a gate is provided on the lower wing plate forming portion side of the mold cavity, a main flow of resin (main flow) occurs in the lower wing plate forming portion and the central support plate forming portion, and the lower side of the gate side Resin from the wing plate forming portion flows into the rib forming portion. As described above, in the rib forming portion, the flow of the resin that is directed upward in the vertical direction can be preferentially generated over the flow of the resin that is directed downward in the vertical direction.

  As a result, the inflow of resin from the central support plate forming portion to the rib forming portion can be effectively suppressed, and in the rib, the weld flow is performed in the central portion in the vertical direction where the generated stress is maximum and in the vicinity thereof. Therefore, the orientation direction of the reinforcing fibers can be set to the vertical direction. Therefore, since the orientation direction of the reinforcing fiber can be matched with the required strength direction of the rib, the strength by the reinforcing fiber can be sufficiently obtained. Moreover, generation | occurrence | production of a micro void can be prevented during injection molding by setting board thickness t1-t3 suitably so that Formula (2)-(4) may be satisfy | filled.

  The matching of the orientation direction of the reinforcing fiber in each of the wing plate, the central support plate, and the rib as described above to the required strength direction, and the setting of the orientation ratios D1 to D3 satisfying the equation (1) are expressed by the equation ( It can implement | achieve effectively by satisfy | filling 2)-(4).

  The stabilizer link manufacturing method of the present invention can use various configurations in order to improve various characteristics. For example, a mode in which the plate thicknesses t1, t2, and t3 are set to 2.0 mm or more can be used. For example, in the longitudinal section of the support bar, a rectangular aspect ratio (= lateral length / longitudinal length) formed by the central portions of the upper wing plate and the lower wing plate and two ribs connected to the central portions. A mode in which the thickness is set within the range of 0.8 to 1.2 can be used.

  For example, the aspect which sets board thickness t1 in the range of 3.0-4.0 mm can be used. For example, in the longitudinal section of the support bar, an aspect ratio of a quadrangle formed by the ends of the upper wing plate and the lower wing plate and two ribs connected to these ends (= lateral length / longitudinal length) The aspect which sets (S) to 0.6 or more can be used. For example, the aspect which sets the minimum value of the curvature radius of the curved part formed in the boundary part of each board of a support bar in the range of 0.5-1.0 can be used.

  According to the stabilizer link of the present invention or the manufacturing method thereof, the required strength of the wing plate and the central support plate in the support bar can be secured, as well as the rib forming portion from the central support plate forming portion in the mold. It is possible to effectively suppress the inflow of resin into the tube and to suppress the occurrence of defects such as weld flow and microvoids, thereby obtaining the effect of ensuring the required strength of the ribs. Can do.

1 is a perspective view illustrating a schematic configuration on a front wheel side of a vehicle. It is a sectional side view showing the schematic structure of an example of the conventional stabilizer link. The schematic structure of the other example of the conventional stabilizer link is represented, (A) is a side view, (B) is a sectional side view of a paper surface perpendicular | vertical direction. It is a sectional side view showing the schematic structure of the left part of the stabilizer link concerning one embodiment of the present invention. The schematic structure of the housing and support bar which were integrally molded in the stabilizer link which concerns on one Embodiment of this invention is represented, (A) is a top view, (B) is a side view, (C) is 5C- of (B). FIG. 5D is a side sectional view taken along line 5C, and FIG. 5D is an enlarged view showing a configuration of a portion surrounded by a frame portion J1 shown in FIG. (A), (B) is an enlarged view showing the structure of the part enclosed by frame part J1, K1 shown to FIG. 5 (B). It is a figure for demonstrating the definition of the orientation rate of the stabilizer link of this invention, (A) is a cross section of the specific example of the reinforced fiber whose angle with respect to a required intensity | strength direction is 45 degrees, (B) is a request | requirement of (A). It is a figure showing the elliptical cross section of the specific example of the reinforced fiber in an intensity | strength direction. The appearance of the stabilizer link of the Example of this invention is represented, the upper photograph of (A) is a perspective photograph, the lower photograph of (A) is a side photograph, (B) is an enlarged photograph for demonstrating an observation part. It is a cross-sectional photograph of the central portion (I portion) of the lower wing plate (gate side wing plate) shown in FIG. 9 is an enlarged cross-sectional photograph of the central portion (I portion) of the lower wing plate shown in FIG. 9, (A) is A portion (left side of the central portion) in FIG. 9, and (B) is B portion (central portion central portion) of FIG. 9. ), (C) is an enlarged cross-sectional photograph of a portion C (right side of the central portion) in FIG. 9. FIG. 9 is a cross-sectional photograph of a portion II of the rib shown in FIG. FIG. 12 is an enlarged cross-sectional photograph of each part in the vicinity of the II part of the rib shown in FIG. 11, (A) is D part (rib side of the lower wing plate) in FIG. 11, and (B) is H part (upper part) in FIG. It is an expanded sectional photograph of the rib side of the wing plate. 11 is an enlarged cross-sectional photograph of a II part of the rib shown in FIG. 11, (A) is an E part (gate side end part) in FIG. 11, (B) is an F part (central part) in FIG. It is an expanded cross-section photograph of 11 G part (opposite side edge part). It is a cross-sectional photograph of the center part (III part) of the center support plate shown in FIG. It is an expanded sectional photograph of each part of the center part (III part) of the center support plate shown in FIG. 14, (A) is I part (center part left side) of FIG. 14, (B) is J part (center) of FIG. Part center) and (C) are enlarged cross-sectional photographs of the K part (right side of the central part) in FIG. It is a graph showing the relationship between the orientation rate and the intensity | strength of resin containing the reinforced fiber in the stabilizer link of the Example of this invention.

(1) Structure and manufacturing method of stabilizer link Hereinafter, an embodiment of the present invention will be described with reference to the drawings. FIG. 4 is a diagram illustrating a schematic configuration of a left side portion of a stabilizer link according to an embodiment of the present invention, and FIG. 5 is a schematic configuration of a housing and a support bar integrally formed in the stabilizer link according to an embodiment of the present invention. FIG. In the stabilizer link 100 of the present embodiment, the same components as those of the stabilizer link 3 of FIG. 2 are denoted by the same reference numerals, and the description thereof is omitted.

  As shown in FIG. 4, the stabilizer link 100 includes a ball stud 110, a ball seat 120, a housing 130, and a dust cover 140. The housings 130 of the stabilizer link 100 are connected by a support bar 140.

  The ball stud 110 has a stud portion 111 and a ball portion 112 made of, for example, metal and integrally formed. The stud part 111 has the taper part 33, the linear part 34, the thread part 35, the collar part 36, and the convex part 37, for example. The ball seat 120 is made of a resin such as POM (polyacetal), for example, and accommodates the ball portion 112 of the ball stud 110. The ball seat 120 has, for example, a flange portion 41 and a heat caulking portion 121.

  The housing 130 has a ball sheet accommodating part 131 that accommodates the ball sheet 120. The side surface portion of the housing 130 has an upper end portion 132 having a flat upper surface, for example. A hole 130 </ b> A is formed at the bottom of the housing 130. A heat caulking portion 121 of the ball seat 120 protrudes through a hole 130 </ b> A at the bottom of the housing 130, and a tip portion of the ball seat 120 engages with a lower surface portion of the housing 130. The dust cover 140 has fixing portions 61 and 62.

  The support bar 150 is a bar integrally formed with the housing 130 as shown in FIG. 5, for example, and has an upper wing plate 151, a lower wing plate 152, a central support plate 153, and ribs 154A to 154F. The configuration and forming method of the support bar 150 will be described in detail below.

  Such a stabilizer link 100 is obtained by the following manufacturing method, for example. First, for example, the upper fixing portion 61 of the dust cover 140 is abutted between the flange portion 36 and the convex portion 37 of the stud ball 201 and is held therebetween. Next, the ball portion 112 of the stud ball 110 is press-fitted into the ball seat 120. In this case, the lower fixing portion 62 of the dust cover 140 is disposed on the lower surface side of the flange portion 41 of the ball seat 120. The ball sheet 120 has a pin portion that becomes the heat caulking portion 121 in a later step.

  Subsequently, an integrally molded housing 130 and support bar 150 are prepared, and the ball sheet 120 is press-fitted into the ball sheet accommodating portion 131 of the housing 130. In this case, the lower fixing portion 62 of the dust cover 140 is sandwiched between the flange portion 41 of the ball seat 120 and the upper end portion 132 of the housing 130, and the pin portion of the ball seat 120 is the hole portion 130 </ b> A of the housing 130. It becomes the form which protrudes from the outside. Next, using a heat caulking machine, the pin portion of the ball sheet 120 is deformed by heating to form a heat caulking portion 121. As a result, the ball seat 120 is fixed to the housing 130, whereby the stabilizer link 100 shown in FIG. 4 is obtained.

(2) Structure and forming method of support bar The wing plates 151 and 152 and the central support plate 153 extend in the longitudinal direction of the support bar 150 as shown in FIG. 5, for example, and are I-shaped in a cross section perpendicular to the longitudinal direction. It has a shape. The central support plate 153 has a function of supporting the wing plate in all parts of the support bar 150 in the longitudinal direction (direction parallel to the x direction). The left and right ribs 154A to 154F in the longitudinal direction of the central support plate 153 are provided between the wing plates 151 and 152 so as to be separated from each other in the longitudinal direction. In this case, the ribs 154A to 154F project in the width direction (direction parallel to the y direction) with respect to the central support plate 153, for example, similarly to the wing plates 151 and 152, and have a function of suppressing the collapse of the wing plates 151 and 152. Have.

  The support bar 150 is made of, for example, a resin integrally formed with the housing 130 and containing reinforcing fibers. The resin material is preferably engineering plastic or super engineering plastic in order to ensure strength, light weight, and improve weather resistance. Examples of the engineering plastic include PA66 (nylon 66), PA6 (nylon 6), PPS (polyphenylene sulfide), and POM (polyacetal). Examples of reinforcing fibers include glass fiber fine fibers.

  The content of the reinforcing fiber in the resin is preferably 25 to 60% by weight. In order that the strength improvement effect by the reinforcing fiber and the strength at high temperature (for example, 80 ° C.) are 50% or more with respect to those at normal temperature (for example, 23 ° C.), the content is preferably set to 25% by weight or more. It is. On the other hand, when the content of the reinforcing fiber is increased, the life of the injection molding machine used for molding is reduced. Therefore, the content is preferably set to 60% by weight or less.

In the upper wing plate 151, the lower wing plate 152, and the central support plate 153, the orientation direction of the reinforcing fibers is set in the longitudinal direction of the support bar 150, and the reinforcing fibers are aligned in the longitudinal direction of the support bar 150. In the ribs 154A to 154F, the orientation direction of the reinforcing fibers is set in the vertical direction (direction parallel to the z direction). In this case, the longitudinal direction orientation ratio D1 (%) of the longitudinal direction center part of the upper wing plate 151 and the lower wing plate 152, the vertical direction orientation ratio D2 (%) of the vertical direction center part of the ribs 154A to 154F, and the ribs 154A to 154F. When the vertical direction orientation rate of the vertical direction end portion is D3 (%), the orientation rates D1 to D3 satisfy the formula (1).
D1>D2> D3 Formula (1)

  It is preferable that the longitudinal direction orientation ratio D1 of the central portion in the longitudinal direction of the upper wing plate 151 and the lower wing plate 152 is set to 60% or more. It is preferable that the longitudinal orientation rate D4 of the central portion of the central support plate 153 in the longitudinal direction is set to 60% or more. It is preferable that the vertical direction orientation ratio D2 of the central portion in the vertical direction of the ribs 154A to 154F is set to 50% or more.

  In this case, for example, in each of the ribs 154A to 154F (only the rib 154A is shown in FIG. 5D), a region having a vertical orientation ratio of 50% or more is formed, and the vertical direction length h1 of the region is vertical. The ratio with respect to the overall length H1 (rib height) is preferably set to 60% or more. In this case, in the above-described region of the rib in which many reinforcing fibers are oriented in the vertical direction, a boundary portion may be formed between the central support plate 152 in which many reinforcing fibers are oriented in the longitudinal direction. Is preferred. The vertical center of the length h1 is located at the vertical center of each rib. FIG. 5D shows the height of the rib at the thickness center line as an example of the overall length H1.

  The housing 130 and the support bar 150 are obtained by injection molding using a mold having a cavity having a shape corresponding to them. In the molding die, the following forming portion of each part is provided in the cavity by using a insert piece or the like. The cavity has a housing forming part for forming the housing 130 and a support bar forming part for forming the support bar 150. The support bar forming portion includes a wing plate forming portion for forming the wing plates 151, 152, a central support plate forming portion for forming the central support plate 153, and a rib forming portion for forming the ribs 154A to 154F. Have.

In order to realize the orientation of the reinforcing fibers in the wing plates 151 and 152, the central support plate 153, and the ribs 154A to 154F as described above, the plate thickness t1 (FIG. 5C) of the wing plates 151 and 152, Corresponding to the channel width of the wing plate forming portion), the thickness t2 of the central support plate 153 (corresponding to the channel width of the central support plate forming portion), and the thickness t3 of the ribs 154A to 154F. (FIG. 5 (B), corresponding to the channel width of the rib forming portion) needs to satisfy the expressions (1) to (3).
t1>t2> t3 Formula (2)
0.77 ≦ t2 / t1 ≦ 0.85 Formula (3)
0.77 ≦ t3 / t2 ≦ 0.85 Formula (4)

  The position of the gate for injecting the resin into the cavity (the position corresponding to the symbol G1 in FIGS. 5B and 5D) is, for example, the longitudinal direction of the lower wing plate forming portion (direction parallel to the x direction). And the central portion in the width direction (direction parallel to the y direction). Note that the gate position (FIG. 5D) is not limited to the central portion in the longitudinal direction and the width direction, and is set within a predetermined length range, for example, in the portion indicated by symbol g of the wing plate forming portion. It only has to be. The center of the symbol g1 is located at the center in the longitudinal direction of the lower wing plate forming portion, for example.

  In this embodiment, when resin is injected from the gate into the cavity of the mold, the resin flows, for example, in the support bar forming portion and the housing forming portion. In this case, the thickness t1 of the upper wing plate and the lower wing plate, the thickness t2 of the central support plate, and the thickness t3 of the plurality of ribs at the support bar forming portion through the housing forming portion so as to satisfy the formula (2). The flow of resin occurs in the order of the wing plate forming portion, the central support plate forming portion, and the rib forming portion, and the resin is filled in the rib forming portion after being filled in the wing plate forming portion and the central support plate forming portion. .

  In this case, in the wing plate forming portion and the central support plate forming portion of the support bar forming portion, the main flow (main flow) of the resin occurs, and the I-shaped wing plates 151 and 152 and the central support plate 153 are the ribs 154A. Preferentially formed over ~ 154F. In this case, since the resin flows in the longitudinal direction in the wing plate forming portion and the central support plate of the cavity, in the wing plates 151 and 152 and the central support plate 153, the orientation direction of the reinforcing fibers is the longitudinal direction of the support bar. Can be set to Therefore, the orientation direction of the reinforcing fibers can be matched with the required strength direction of the wing plates 151 and 152, so that the strength by the reinforcing fibers can be sufficiently obtained.

  Here, in the lower wing plate forming portion and the central support plate forming portion, when the main flow of resin occurs, the resin from the gate side lower wing plate forming portion flows into the rib forming portion. As described above, in the rib forming portion, the flow of the resin that is directed upward in the vertical direction can be preferentially generated over the flow of the resin that is directed downward in the vertical direction. As a result, the inflow of resin from the central support plate forming portion to the rib forming portion can be effectively suppressed, and in the rib, the weld flow is performed in the central portion in the vertical direction where the generated stress is maximum and in the vicinity thereof. Therefore, the orientation direction of the reinforcing fibers can be set to the vertical direction. Therefore, since the orientation direction of the reinforcing fiber can be matched with the required strength direction of the rib, the strength by the reinforcing fiber can be sufficiently obtained. Moreover, generation | occurrence | production of a micro void can be prevented during injection molding by setting board thickness t1-t3 suitably so that Formula (2)-(4) may be satisfy | filled.

  The wing plates 151, 152, the central support plate 153, and the ribs 154A to 154F as described above match the orientation direction of the reinforcing fibers in the required strength direction, and the orientation ratios D1 to D1 satisfying the formula (1) The setting of D3 can be effectively realized by satisfying the expressions (2) to (4).

  In particular, when the vertical direction orientation ratio D2 of the central portion in the vertical direction of the ribs 154A to 154F is set to 50% or more, the ribs 154A to 154F can further obtain strength due to the reinforcing fibers. When the longitudinal direction orientation ratio D1 at the longitudinal center part of the upper wing plate 151 and the lower wing plate 152 is set to 60% or more, the wing plates 151 and 152 can further obtain strength due to reinforcing fibers. When the longitudinal direction orientation rate D4 of the central portion in the longitudinal direction of the central support plate 153 is set to 60% or more, the strength of the reinforcing fibers can be further obtained in the central support plate 153.

  In the injection molding as described above, it is preferable to satisfy the following conditions in order to improve the performance of the support bar 150. In order to secure the moldability (resin fluidity) of the support bar 150, it is preferable to set the plate thicknesses t1 to t3 to 2.0 mm or more.

  The interval between the ribs 154A to 154F is preferably set as follows.

  In the conventional stabilizer link 5 shown in FIG. 3, in the quadrangle surrounded by the plate thickness center line of the upper wing plate 91 and the lower wing plate 92 and the plate thickness center line of the ribs 94A, 94B, the interval between the ribs 94A, 94B is the wing plate. If it is too larger than the distance between 91 and 92, the wing plates 91 and 92 may fall (distort) around the vicinity of the central portion in the longitudinal direction. For example, in the stabilizer link 5, assuming that the longitudinal interval between the wing plates 91 and 92 is l1 and the lateral interval between the ribs 94A and 94B is l2, the spacing ratio (= lateral interval l2 / longitudinal interval l1) is 2.5. Therefore, there is a high possibility that the wing plates 91 and 92 fall between the ribs 94A and 94B.

  In contrast, in the present embodiment, the ribs 154A to 154F are provided between the wing plates 151 and 152 so as to be equally spaced from each other in the longitudinal direction. In this case, the following aspect is preferable for the ribs 154A to 154F. It is.

  For example, as shown in FIG. 6A, in the longitudinal section of the support bar 150, when the quadrilateral is formed by the central portions of the wing plates 151 and 152 and the two ribs 154A and 154A connected to the central portions, It is preferable to set the aspect ratio of the quadrangle (= horizontal length s2 / vertical length s1) within a range of 0.8 to 1.2. 6A is the thickness center line of each plate, and the length s1 is the distance between the intersections of the thickness center line of the rib 154A and the thickness center lines of the wing plates 151 and 152. The length s2 is the distance between the plate thickness center lines of the ribs 154A and 154A.

  In the above square, the wing plates 151 and 152 are less likely to fall down as the aspect ratio approaches 1.0. In the support bar 150, for example, the portion where the stress is highest when receiving a buckling load is the central portion, and therefore the aspect ratio of the quadrilateral is important. On the other hand, if the interval between the ribs 154A and 154A is too short, the configuration of the mold becomes complicated. In order to suppress these problems, the above aspect ratio range is preferable.

  Since the buckling stress is low on the end side of the support bar 150, the interval between the ribs may be set large. In this case, for example, when a square is formed by the end portions of the wing plates 151 and 152 and the two ribs 154E and 154F connected to the end portions in the longitudinal section of the support bar 150 shown in FIG. It is preferable to set the aspect ratio of the quadrangle (= horizontal length s4 / vertical length s3) to 0.6 or more. The broken line in FIG. 6B is the plate thickness center line of each plate, and the length s3 is the intersection of the plate thickness center line of the ribs 154E and 154F and the plate thickness center line of the wing plates 151 and 152. The distance s4 is the distance between the plate thickness center lines of the ribs 154E and 154F.

  It is preferable to set the plate thickness t1 of the wing plates 151 and 152 within the range of 3.0 to 4.0 mm. If the plate thickness t1 of the wing plates 151 and 152 is too thick, microvoids may occur during injection molding, and the original strength that can be exhibited by the reinforcing fibers may not be obtained, and the weight can be sufficiently reduced. Is difficult. In order to eliminate such a problem, it is preferable to set the plate thickness t1 to 4.0 mm or less. Moreover, in order to ensure moldability (resin fluidity) more effectively, it is preferable to set the plate thickness t1 to 3.0 mm or less.

  It is preferable that the radius of curvature of the portion of the curved portion formed at the boundary portion of each plate of the support bar 150 that has the smallest radius of curvature is set in the range of 0.5 to 1.0. In this aspect, since the resin flows smoothly, the reinforcing fibers can be aligned in the required strength direction on each plate.

  Hereinafter, embodiments of the present invention will be described in more detail with reference to specific examples. In the example, the stabilizer link shown in FIG. 8A was obtained using the manufacturing method of the embodiment. In the manufacture of stabilizer links, nylon 6 or nylon 66 was used as the resin, and glass fiber fine fibers were used as the reinforcing fibers to be contained in the resin. The content of reinforcing fibers in the resin was set to 30 to 60% by weight.

  About the stabilizer link obtained in this way, using SEM, as shown in FIG. 8 (B), the longitudinal direction portion (I portion) of the lower wing plate (gate side wing plate) in the longitudinal center portion of the support bar The cross section of the II part of the rib (corresponding to the reference numeral 154A in FIG. 5B) and its vertical part and the longitudinal part (III part) of the central support plate were observed. The results are shown in FIGS.

  9 to 15, the vertical relationship of the wing plates is the same as the embodiment, with the gate side being the lower side and the side opposite to the gate side being the upper side, and the upper and lower sides are reversed. The horizontal direction corresponds to the longitudinal direction of the support bar, and the vertical direction corresponds to the vertical direction of the support bar. The bright part in the photograph shows the reinforcing fiber. In the following, the orientation ratio of reinforcing fibers is shown for a predetermined portion of each plate, and the method described in [0021] to [0024] of the present application was used as the measurement method. In this case, the orientation rate in the 0.5 mm square (0.5 mm × 0.5 mm region) of the central portion of each photograph was examined. FIG. 16 is a graph showing the relationship between the orientation rate and strength of a resin containing reinforcing fibers. When the orientation rate is 100%, the angles with respect to the required strength direction are −45 ° or more for all the reinforcing fibers. This is a case where it is within a range of 45 ° or less.

  FIG. 9 shows the cross-sectional observation result of the I part (FIG. 8B) of the lower wing plate, and FIGS. 10A to 10C show the enlarged cross-sectional observation result of the A part to the C part of FIG. Represents. As can be seen from FIGS. 10 (A) to 10 (C), in the I part of the lower wing plate, the orientation direction of the main reinforcing fibers was the lateral direction (longitudinal direction). The longitudinal direction orientation ratio (D1) of B part (center part) of I part of the lower wing plate shown in FIG. 10B was 69.2%, and the strength was 92.3%.

  11 shows a cross-sectional observation result of the II part of the rib and the vicinity thereof (FIG. 8B), and FIGS. 12A to 12C show the D part, the H part, and the E part of FIG. The enlarged cross-section observation result of G section is represented. 11 is a rib side portion of the lower wing plate, H portion of FIG. 11 is a rib side portion of the upper wing plate, and E portion to G portion in FIG. 11 are lower wing plate side end portions (gates) of the rib. Side end part), vertical center part of the rib, and upper wing plate side end part (opposite end part) of the rib. The orientation direction of the reinforcing fibers in the D part (rib side part) of the lower wing plate and the H part (rib side part) of the upper wing plate was not the longitudinal direction (vertical direction), whereas the lower wing plate side of the rib The end portion (E portion), the rib F portion (vertical center portion), and the rib G portion (upper wing plate side end portion) are as shown in FIGS. The orientation direction of the reinforcing fibers was the longitudinal direction (vertical direction). In particular, in the E part (lower wing plate side end part) of the rib and the G part (upper wing board side end part) of the rib, the closer to the F part (vertical center part) of the rib, the more reinforcing fibers are in the vertical direction (vertical). Direction) was strong.

  The vertical orientation ratio (D2) of the vertical central portion (F portion) of the rib shown in FIG. 13B was 55%, and the strength was 88.8%. The vertical orientation ratio (D3) of the lower wing plate side end portion (E portion) shown in FIG. 13A was 16%, and the strength was 78.8%. The vertical orientation rate of the rib side portion (D portion) of the lower wing plate shown in FIG. 12A was 6%, and the strength was 76.6%.

  FIG. 14 shows a cross-sectional observation result of III part (FIG. 8B) of the central support plate, and FIGS. 15A to 15C show enlarged cross-sectional observation results of I part to K part of FIG. Represents. In part III of the central support plate, as can be seen from FIGS. 15A to 15C, the orientation direction of the main reinforcing fibers was the transverse direction (longitudinal direction). The longitudinal orientation ratio (D4) of the J portion (center portion) of the I portion of the central support plate shown in FIG. 15B was 68%, and the strength was 91.7%.

  As described above, in the present embodiment, the reinforcing fibers are mainly oriented in the longitudinal direction in the upper wing plate, the lower wing plate, and the central support plate, and the reinforcing fibers are mainly oriented in the vertical direction in the ribs. It was confirmed. In this case, the longitudinal direction orientation ratio D1 (%) of the longitudinal center part (B part) of the lower wing plate, the vertical orientation ratio of the perpendicular center part (F part) of the rib is D2, and the vertical end part ( It was confirmed that the orientation ratios D1 to D3 satisfy the formula (1) when the vertical orientation ratio of E part) is D3.

  In this case, the vertical orientation rate D2 of the vertical center portion (F portion) of the rib can be set to 50% or more, and the longitudinal orientation rate D1 of the longitudinal center portion (B portion) of the lower wing plate is set to 60. It was confirmed that the longitudinal orientation ratio D4 of the central portion (J portion) in the longitudinal direction of the central support plate can be set to 60% or more.

  DESCRIPTION OF SYMBOLS 100 ... Stabil link, 110 ... Ball stud, 111 ... Stud part, 112 ... Ball part, 120 ... Ball seat, 130 ... Housing 130, 131 ... Ball sheet accommodating part, 132 ... Upper end part, 140 ... Dust cover, 150 ... Support Bar, 151 ... Upper wing plate, 152 ... Lower wing plate, 153 ... Center support plate, 154A to 154F ... Rib, G1 ... Position corresponding to gate, t1 ... Plate thickness of wing plate, t2 ... Plate thickness of center support plate , T3 ... rib thickness

The present invention relates to a stabilizer link having a support bar, and more particularly to improvement of a resin-made support bar.

Accordingly, an object of the present invention is to provide a stabilizer link capable of ensuring the required strength of the rib as well as the required strength of the wing plate and the central support plate in the support bar. .

The manufacturing method of the stabilizer link as described above is to form a support bar by performing injection molding by injecting resin into the mold cavity from the gate, and in the formation of the support bar, an upper wing plate, a lower wing plate, The central support plate is formed to extend in the longitudinal direction of the support bar and have an I shape in a cross section perpendicular to the longitudinal direction, and a plurality of ribs are formed between the upper wing plate and the lower wing plate. When formed so as to be separated from each other in the longitudinal direction, the thickness of the upper wing plate and the lower wing plate is t1, the thickness of the central support plate is t2, and the thickness of the plurality of ribs is t3, the plate thicknesses t1, t2, t3 is set to satisfy the equation (1) to (3).
t1>t2> t3 Formula (2)
0.77 ≦ t2 / t1 ≦ 0.85 Formula (3)
0.77 ≦ t3 / t2 ≦ 0.85 Formula (4)

In the stabilizer link manufacturing method as described above, the orientation direction of the reinforcing fiber of each plate is made to coincide with the required strength direction as in the stabilizer link of the present invention, and the longitudinal orientation ratio D1 of the longitudinal center portion of the wing plate, the rib In order to control the flow of the resin so that the vertical direction orientation ratio D2 of the vertical center portion of the rib and the vertical direction orientation ratio D3 of the vertical end portion of the rib satisfy the formula (1), an upper wing plate, a lower wing plate, A relational expression of the thickness of each of the central support plate and the rib is set.

Here, in the manufacturing method of the stabilizer link, thin plate thickness of the central support plates than wing plate, and by setting the thicker plate thickness than the ribs, than the rib wing plate and central support plate which forms an I-shape It can be preferentially formed. In this case, for example, if a gate is provided on the lower wing plate forming portion side of the mold cavity, a main flow of resin (main flow) occurs in the lower wing plate forming portion and the central support plate forming portion, and the lower side of the gate side is formed. Resin from the wing plate forming portion flows into the rib forming portion. As described above, in the rib forming portion, the flow of the resin that is directed upward in the vertical direction can be preferentially generated over the flow of the resin that is directed downward in the vertical direction.

The manufacturing method of the stabilizer link can use various configurations in order to improve various characteristics. For example, a mode in which the plate thicknesses t1, t2, and t3 are set to 2.0 mm or more can be used. For example, in the longitudinal section of the support bar, a rectangular aspect ratio (= lateral length / longitudinal length) formed by the central portions of the upper wing plate and the lower wing plate and two ribs connected to the central portions. A mode in which the thickness is set within the range of 0.8 to 1.2 can be used.

Claims (12)

It is formed by injection molding using a resin containing reinforcing fibers, and includes a support bar for connecting the housings together.
The support bar has an upper wing plate, a lower wing plate, a central support plate, and a plurality of ribs,
The upper wing plate, the lower wing plate, and the central support plate extend in the longitudinal direction of the support bar and have an I-shape in a cross section perpendicular to the longitudinal direction, and the plurality of ribs are The upper wing plate and the lower wing plate are provided so as to be separated from each other in the longitudinal direction,
In the upper wing plate, the lower wing plate, and the central support plate, the reinforcing fibers are oriented in the longitudinal direction, and in the ribs, the reinforcing fibers are oriented in the vertical direction,
The longitudinal orientation rate of the longitudinal central portion of the upper wing plate and the lower wing plate is D1 (%), the vertical orientation rate of the vertical central portion of the rib is D2 (%), and the vertical end portion of the rib A stabilizer link characterized in that the orientation ratios D1 to D3 satisfy the formula (1) when the vertical direction orientation ratio is D3 (%).
D1>D2> D3 Formula (1)   2. The stabilizer link according to claim 1, wherein a vertical direction orientation ratio D <b> 2 of a vertical central portion of the rib is set to 50% or more.   3. The stabilizer link according to claim 1, wherein a longitudinal direction orientation ratio D <b> 1 of a longitudinal center portion of the upper wing plate and the lower wing plate is set to 60% or more.   The stabilizer link according to any one of claims 1 to 3, wherein a longitudinal orientation ratio D4 of a central portion in the longitudinal direction of the central support plate is set to 60% or more.   The stabilizer link according to any one of claims 1 to 4, wherein a content of the reinforcing fiber in the resin is 25 to 60% by weight.   6. The stabilizer link according to claim 1, wherein the resin is engineering plastic or super engineering plastic. In the manufacturing method of the stabilizer link in any one of Claims 1-6,
The support bar is formed by injecting the resin from the gate into the mold cavity and performing injection molding,
In forming the support bar, the upper wing plate, the lower wing plate, and the central support plate are formed so as to extend in the longitudinal direction of the support bar and have an I-shape in a cross section perpendicular to the longitudinal direction. And forming the plurality of ribs such that the upper wing plate and the lower wing plate are separated from each other in the longitudinal direction,
When the plate thickness of the upper wing plate and the lower wing plate is t1, the plate thickness of the central support plate is t2, and the plate thickness of the plurality of ribs is t3, the plate thicknesses t1, t2, and t3 are expressed by the formula (1). The manufacturing method of stabilizer link characterized by satisfying (3).
t1>t2> t3 Formula (2)
0.77 ≦ t2 / t1 ≦ 0.85 Formula (3)
0.77 ≦ t3 / t2 ≦ 0.85 Formula (4)   The method for manufacturing a stabilizer link according to claim 7, wherein the plate thicknesses t1, t2, and t3 are set to 2.0 mm or more.   A rectangular aspect ratio (= lateral length / longitudinal direction) formed by a central portion of the upper wing plate and the lower wing plate and two ribs connected to the central portion in a longitudinal section of the support bar. 9. The method for manufacturing a stabilizer link according to claim 7 or 8, wherein the length is set within a range of 0.8 to 1.2.   The method for manufacturing a stabilizer link according to any one of claims 7 to 9, wherein the plate thickness t1 is set within a range of 3.0 to 4.0 mm.   A rectangular aspect ratio (= lateral length / longitudinal direction) formed by the end portions of the upper wing plate and the lower wing plate and two ribs connected to the end portions in the longitudinal section of the support bar. The manufacturing method of the stabilizer link according to any one of claims 7 to 10, characterized in that the length is set to 0.6 or more.   The minimum value of the curvature radius of the curved part formed in the boundary part of each board of the said support bar is set in the range of 0.5-1.0, The any one of Claims 7-11 characterized by the above-mentioned. Method of manufacturing stabilizer links.

Images